Apparatus for producing gas under pressure



Dee. 18, 1951 M, KADENACY 2,579,321

APPARATUS FOR PRODUCING GAS UNDER PRESSURE Filed April 9, 1948 4Sheets-Sheet 1 RECEIVER I j RECEIVE? 43 43 l runs/ms I I, I J0 flwwmj d/l 4 km 2 22:? H BY 0 i a m fl vi ATTORNEYS Dec. 18, 1951 M. KADENACY 72,579,321

' APPARATUS FOR PRODUCING GAS UNDER PRESSURE 1 Filed April 9, 1948 I 4Shets-Sheet 3 ATTORNEYS Patented Dec. 18, 1 951 mans-ms roa monucmc GASunnaa rasssuaa I were! Kadenacy. Summit, N. 1.; Nina x. Guorckenexecutrix of said Michel Kadenacy, deceased Application April 9, 1948,Serial No. 19,973

13 Claims.

This invention relates to apparatus of the kind which includes a gasturbine of the constant volume explosive combustion type and isconcerned more particularly with a novel apparatus for producing asupply of gases under pressure or moving at high velocity, which may beused for Jet propulsion, for the operation of a prime mover, such as aturbine, or for other purposes. The new gas producing apparatus is ofsimple construction with few movingparts and it can be built andoperated. at low cost. The apparatus requires little attention inservice and may be run for long periods without interruption and at highefiiciency.

The apparatus of the invention includes a plurality of elongatedcombustion chambers arranged in a circular series with theirlongitudinal axes parallel and each chamber has an inlet orifice and 'anoutlet orifice in its side wall facing outwardly at opposite ends of thechamber. A pair of rotors are mounted at opposite ends of the series ofchambers for'rotation in unison on the central axis of the series andeach rotor has a portion overlying the orifices at the adjacent ends ofthe chambers and one or more openings in that portion, which registerwith the orifices in successive chambers along the series, as the rotorrotates. The inlet and exhaust orifices" of each chamber are of suchsize in relation to the transverse cross-sectional area of the chamberas to be suitable for introduction of fresh charges into the chamber andthe discharge of burned gases therefrom in accordance with the naturalphenomena of implosive inlet and explosive exhaust, respectively.Thechambers are supplied with air under pressure and with fuel and thecombustible charges are ignited by auto-ignition or by suitable ignitionmeans. The burned gases are discharged from the chambers through exhaustpipes and, in a jet propulsion apparatus, the gases are utilized tooperate a turbine driving a compressor supplying air under pressure tothe combustion chambers, and are then passed through a common nozzle tothe atmosphere. In a power plant, in which the gases are to be employedunder pressure, the gases may be used to drive a compressor, if desired,and are stored under pressure in a receiver, which is connected to theinlet of the prime mover.

In the operation of the new apparatus, combustible charges of fuel andair are ignited successively in the chambers along the series, and, whena charge in a chamber is in process of combustion or combustion of sucha charge is substantially complete, the exhaust orifice of the chamberis opened to such an extent and in so short an interval of time, thatthe burned gases leave the chamber in accordance with the phe-- nomenonof explosion at ballistic speed as part the inlet orifice of the chamberis opened to such 4 an extent and in so short an interval that a freshgaseous charge enters the chamber in accordance with the phenomenon ofimplosive in- I let. Preferably, both orifices o! the chamber aremaintained open to permit a substantial quantity of inlet air to pass.through the chamber and into the exhaust pipe connected thereto. When apredetermined quantity of air has thus passed through the chamber, theexhaust orifice is quickly closed and theinlet orifice is quickly closedshortly thereafter. As a result of closing the orifices as described,the chamber is supercharged by the ramming eilect of the mass of theinlet air against the closed exhaust orifice and the quick closing ofthe inlet orifice traps the air within the chamber, so that the finalpressure within the chamber is greater than the pressure of the inletair at the source. Fuel is then injected into the chamber to form acombustible mixture, the mixture is ignited, and the cycle is complete.The cycle of operations above described in connection with one chamberis carried on in each chamber along the series with the cycles startingone after another in successive chambers.

For a better understanding of the invention, reference may be had to theaccompanying drawings, in which Fig. 1 is a plan view of a power plantembody- I ing the invention;

Fig. 2 is a longitudinal vertical section through the gas producingapparatus of the plant of Fic- Fig. 2a is a sectional view on the linela-Ia of Fig. 2;

Figs. 3 and 4 are sectional views on the lines 3-3 and 4-4 of Fig. 2,respectively;

Figs. 5 and 6 are diagrammatic views showing the operation of therotors;

Fig. '7 is a view partly in section and partly in side elevation ofanother form of power plant embodying the invention;

.Fig. 8 is a sectional view on the line 8-8 of Fig.7;

Fig. 9 is a fragmentary elevational view illustrating another means forpreventing the return of gases to the combustionchambers;

Fig. is a sectional view on the line lO-ll of Fig. 9; and

Fig. 11 is a view, partly in elevation and partly in longitudinalsection, of a Jet propulsion apparatus embodying the invention.

The power plantillustrated in Fig. 1 comprises a blower or compressorIn, which supplies compressed air to a receiver H connected by pipes l2to a plurality of combustion chambers of the gas producing apparatus,which is generally designated l3.

The gas producing apparatus illustrated comprises a casing ll containingwalls defining four elongated combustion chambers ll arranged in acircular series with their longitudinal axes parallel Each chamber isprovided with an inlet orifice l8 and an exhaust orifice IT at oppositeends thereof, the orifices being formed in the side wall of the chamberand facing outwardly.

The cross-section of each chamber may be gen-' erally rectangular orsmoothly curved in outline, with a circular cross-section preferred. Thecross-section of the chamber should not change abruptly along itslength, but the cross-section may decrease toward the exhaust orifice ata rate such that, in the case of a chamber of circular cross-section,the chamber has a conicitv of about 1% to 2%. Each orifice may becircular but is preferably generally rectangular and its dimensions arepreferably such that its cross-sectional area is approximately eoual toor greater than the transverse cross-sectional area of its chamber andits dimension transverse to the chamber is smaller than its dimensionlen thwise of the chamber. The casing is formed with inlet passages 18.which are connected to respective air supplv pipes l2 and lead toindividual inlet orifices l8, and means, such as vanes Ha, for causingair to enter the chamber with a swirling movement, may be mounted ineach inlet passage adiacent its inlet orifice. The casing is providedwith an exhaust passage l9 leading from each exhaust orifice I1.

A shaft extends through the casing with its axis coincident with thecentral axis of the series of chambers and is supported for rotation inbearings 2| at opposite ends of the casing and is driven by a suitableelectric or gas-driven motor 22. At the ends of the chambers having theinlet orifices iii, the shaft carries a rotor 23, which includes aradial portion 24 attached to the shaft and a portion 25 concentric withthe shaft and of cylindrical or conical form (see Figs. 2 and '7). Theportion of the rotor concentric with the shaft overlies the inletorifices and extends into a circular recess 26 formed in a wall of thecasing. Any suitable means are provided for sealing the rotor to'preventescape of gases along the rotor to the shaft and, for this purpose, thecasing may be formed with walls 21. 28 lying close to the inher andouter surfaces of the rotor and the radial portion of the rotor may beprovided with concentric ribs 29 entering corresponding grooves in walls21, 28 to form a labyrinth seal. The portion of the inlet rotor 23,which is concentric with the shaft, is provided with oppositely disposedopenings 23a, each of which is of approximately the same dimensionlengthwise of the chambers as the inlet orifices it, but issubstantially longer circumferentially than the corresponding dimensionof the individual orifices.

The shaft 20 carries a second rotor 30 at the ends of the chambersprovided with the exhaust orifices and the exhaust rotor 20 is of thesame 23, except that the openings "a in the exhaust rotor are oflsetangularly ahead of the corresponding openings in the inlet rotor.

The walls of the chambers and of the inlet and exhaust passages and theend walls of the casing may be cooled by air or by a cooling fluid and,in the construction illustrated, the walls are jacketed to form spaces3|, through which a cooling medium may be circulated. The fluid, whichmay be water, may be supplied through inlet 32 and withdrawn throughoutlet 33. A fuel nozzle 34 is mounted in an opening through the wallsof each chamber and is connected by a line 35 to a fuel pump of anysuitable type. The nozzle 'atomizes fuel into the chamber, whenever acharge of fuel is supplied thereto by the pump.

7 Each chamber is also provided with ignition means, illustrated as aspark plug 38.

The combustion chambers ll of the gas producing apparatus are preferablyof like crosssectional area and the exhaust orifices of the chambers areof like size. Also, the cross-sectional area of each exhaust orificebears such relation to the transverse cross-sectional area 01' itschamber that it is possible to cause discharge of the burned gases fromthe chamber as a mass at ballistic speed in accordance with thephenomenon of explosive exhaust. As explained in a number of my priorpatents. such as Patent 2123569, it is necessary, in order to obtainexplosive exhaust of the burned gases from such a combustion chamber,that the exhaust orifice be opened to a critical extent in a criticaltime interval. The extent, to which the orfice must thus be opened, isat least A and preferably more than /2 of the transverse cross-sectionalarea of the chamber and the orifice should be opened in an interval ofabout 600 second or less. When such an exhaust orifice is so opened, thetotal mass of the burning gases begins to react upon the chamber wallsand is accelerated in a direction out of the chamber through the exhaustorifice. When the gases have been sufliciently accelerated and haveacquired sufllcient speed, they cease reacting upon the chamber wallsand begin to move out of the chamber in a mass at ballistic speed byvirtue of their momentum, leaving a potential void behind in thechamber.

The inlet orifices of the combustion chambers are of like size and thecross-sectional area of each inlet orifice bears such relation to thetransverse cross-sectional area of its chamber that it is possible tocause air from the receiver II to be introduced into each combustionchamber in a dense mass at ballistic speed in accordance with thephenomenon of implosive inlet. The conditions required to obtainimplosive inlet are explained in my Patent 2,281,585 and they involveopening the inlet orifice to a critical extent in a critical timeinterval. The critical opening of an inlet orifice for implosive inletis at least $4; and preferably more than V: of the transversecrosssectional area of the chamber and such an orifice should thus beopened in an interval of about /200 second or less. The air inlet pipesl2 of the apparatus are of such form, as explained in Patent 2,281,585,as to facilitate supercharging of each chamber, that is, introducing airinto the chamber by implosive inlet in such manner, that the pressure ofthe charge in the chamber is higher than that of the pressure inreceiver I I.

Each exhaust passage l9 leading from the combustion chamber is connectedby an exhaust pipe 39 to an exhaust gas receiver 40, which is, in

general shape and construction as the inlet rotor turn, connected by apipe 4| to the inlet of a turearnest blue 82. The shaft Q3 of theturbine may be utilized to drive any desired machine.

In the operation of the apparatus illustrated, the cycle of operationsin a given combustion chamber may be assumed to start with ignition of acharge of combustible mixture in that chain ber. Such ignition may beinitiated by the tern perature of the air in the chamber at the time thefuel is injected or by ignition means, such as a spark plug. When thecharge in the chamber is in process of combustion or combustion issubstantially complete, the rotation of exhaust rotor 3@ brings one ofits openings 36a into registry with the exhaust orifice ll of thechamber and the orifice is opened within the critical conditions forexplosive exhaust. Upon the opening of the orifice, the total mass ofthe burning gases within the chamber begins to react upon the chamberwalls and is accelerated in a direction toward the exhaust orifice.During this period of acceleration of the gases, an acceleration fronttravels through the inert gases in the exhaust passage 89 leading fromthechamber and the exhaust pipe 35 connected to that passage.Ultimately,

the gases in the chamber acquire such speed that they cease reactingupon the chamber walls and start to move out of the chamber by virtue oftheir momentum as part of an exhaust gas mass, which includes the burnedgases and the inert gases in the exhaust passage and pipe connected tothe chamber, which have been accelerated thereby during the period ofacceleration of the burned gases, The leading end of such an exhaust gasmass lies at the point, which has been reached by the acceleration fronttraveling through the inert gases at the time that the gases ceasereacting upon the chamber walls and the period of acceleration thereofterminates.

Each exhaustgas mass produced during explosive exhaust from a combustionchamber travels through the exhaust passage leading from that chamberand the exhaust pipe connected to the passage and to the gas receiver.For best conditions of operation, the cross-sectionl area or" theexhaust orifice of a chamber should be substantially the same as thetransverse cross-sectional area of the adjacent end of the chamber andthe rotor should be so constructed and operd an exahust gas mass hasbeen converted into potential energy, a static rebounding pressure frontis formed in'the inert gases being displaced by the exhaust gas mass andthis pressure front immediately explodes, with part of the explodinggases returning toward the exhaust orifice of the combustion chamber. Itis important that the gases returning from the static reboundingpressure front be prevented from returning through the exhaust pipe andreentering the chamber through the exhaust orifice and, by properlyconstructing the exhaust pipe, as above explained, the outward movementof the exhaust gases may be prolonged and the distance between the charmbar and the place of-formation of the static rebounding pressure frontincreased. The time interval between the mass exit of the gases from thechamber and the return of the gases from the static rebounding pressurefront is then, correspondingly, increased. In some instances, it

' may be desirable to provide means between the ated that the orificewill be fully opened at the moment when the burned gases begin to leavethe chamber as a mass. The cross-sectional area of the exhaust passageshould be substantially the same as that of the exhaust orifice and thecrosssectional area of the exhaust pipe at its end adjacent the exhaustpassage should be substantially the same as that of the passage. Thecross-sectional area of the pipe may increase slightly, either graduallyor in steps, toward its end connected to the receiver. When the exhaustpassage and the exhaust pipe are formed, as described, they provide afree passage" for exhaust gas masses therethrough, in that the outwardtravel of the exhaust gas masses from the combustion chamber throughsuch a passage is against a minimum resistance of inert gases per unitlength of travel of the exhaust gas masses. Also, those masses, whileconfined in such a free passage against lateral expansion, can traveltherethrough with a minimum frictional resistance.

As each exhaust gas mass travels outwardly through an exhaust pipe 38,it displaces inert gases ahead of. it and its dynamic energy isconverted into potential energy of gas pressure during such action. Whenall the dynamic energy of chambers and the exhaust gas receiver forpreventing the return of the gases, and one form of such means isillustrated in the power plant shown in Fig. '7.

The power plant illustrated in Fig. 7 includes an air compressor M, theoutlet of which is connected by a pipe 5 to a compressed air receivertil, from which a plurality of pipes til lead to the respective inletorifices of combustion chambers of a gas producing device, generallydesignated 39. Each chamber has an exhaust orifice adjacent one end,which is slightly smaller than the inlet orifice /of the chamber, andthe chambers are of gradually decreasing cross-section toward theirexhaust orifices. The inlet and exhaust orifices are controlled byrespective rotors &9, 56 mounted on a shaft 5% driven by a motor Therotors have radial portions attached to the shaft iii and conicalportions, which overlie the orifices and have openings registering withthe orifices during the rotation of the rotors. An exhaust pipe tilleads from the exhaust orifice of each chamber to a separate inlet of acasing 56 containing an impulse turbine wheel mounted on the shaft 56carrying the rotors of compressor 3 3.. The gas producing apparatuscomprises four combustion chambers, each of which is provided with afuel injection nozzle 57 and a spark plug 5%. The chambers are arrangedin a circular series with their longitudinal axes parallel and theinlets of casing 5d are arranged in a circular series on equal spacings.The casing 54, has an annular outlet 59 connected by a pipe Ell to anexhaust gas receiver 6!, from which a pipe 62 leads to the inlet of amulti-stage turbine 63.

The construction of the impulse turbine wheel 55 is such that eachexhaust gas mass leaving a chamber of the gas producing apparatus d8acts on the blades of the wheel and rotates the wheel at high speed. Thetotal cross-sectional area of the spaces between the blades of wheel 55in line with each inlet of casing 54 is substantially the same as thecross-sectional area of the pipe 53 leading to that inlet, so that thereis a free passage for each gas mass through the wheel. The outlet 59from casing 54 and pipe 60 are so formed as to constitute a prolongationof the free passage.

The impulse turbine wheel is disposed at approximately the leading endof each exhaust gas mass about to travel away from a combustion chamberat the time that the burned gases stop reacting upon the chamber wallsand the mass,, begins to move by virtue of its momentum. The

wheel is thus approximately at the point reached by the accelerationfront traveling through the inert gases in a pipe 53 at the time thatthe period of acceleration of the burned gases in a combustion chamber,from which that pipe leads, comes to an end. By placing the turbinewheel at the critical point specified, each exhaust gas mass acts in itsentirety on the wheel and the action starts coincidentally withbeginning of movement of the mass away from the chamber. Accordingly.each exhaust gas mass acts on the wheel with maximum dynamic energy andthe wheel is rotated at high speed. As each exhaust gas mass travelsthrough the wheel, the casing outlet 59, and pipe 60 and a staticrebounding pressure front is formed in either pipe 60 or the exhaust gasreceiver 6!, the gases returning from the static rebounding pressurefront upon the explosion thereof are unable to pass through the wheeland re-enter the chambers.

In the modified construction shown in Figs. 9 and 10, the exhaust pipes64 lead from combustion chambers (not shown) to inlets in an end wall 65of an exhaust gas receiver '66. The inlets are disposed in a circularseries in the end wall nd are offset angularly from the main lengths ofthe exhaust pipes 64 leading thereto. Each exhaust pipe has a curved endportion 61 connected to its inlet and the curved portions extend in thesame direction from their respective pipes to the inlets, so that, eachexhaust gas mass enters the receiver in a tangential direction and thusrotates within the receiver. Successive exhaust gas masses entering thereceiver maintain the rotating gas mass and the gases, which return fromthe static rebounding pressure front, upon the explosion of the latter,are unable to pass through the rotating gas mass and enter an exhaustpipe. The receiver is preferably so disposed that the inlets in its endwall 65 lie at approximately the leading end of each exhaust gas mass atthe time the burned gases forming part of that mass cease reacting uponthe walls of a chamber and the mass begins to move out of and away fromthe chamber because of its momentum. As a, result, each exhaust gas massbegins its rotational movement within the receiver at the time that themass has maximum momentu and the rotating body of gas within thereceiver, accordingly, has maximum rotational speed.

The jet propulsion apparatus illustrated in Fig. 11 includes a gasproducing apparatus 68 having a plurality of combustion chambers, towhich air is supplied under pressure through inlet pipes '69. The fuelis injected into the chambers through nozzles and the combustiblecharges are ignited by spark plugs II. The inlet and exhaust rotorscontrolling the orifices of the chambers are rotated by a motor I2. Theexhaust pipes 13 leading from the individual chambers deliver theexhaust gases to respective inlets in a casing 14 containing an impulseturbine wheel 15, the shaft I6 of which is connected to the rotor of acompresor ll delivering air under pressure to a receiver (not shown),from which the inlet pipes 69 lead. The gases issuing from casing 14 aredischarged through a. common nozzle 18, which contains a cone deflector19. The gas producing apparatus employed in the construction shown inFig. 11 is built and operated in accordance with the principles aboveset forth and the impulse turbine wheel 15 is preferably disposed atsuch a distance from the combustion chambers that it lies at thelocation of the leading end of each exhaust gas mass about to travelaway from a chamber at the time that the burned gases forming part ofthat mass stop reacting upon the chamber walls. The wheel is thusmaintained in high speed rotation and prevents the return of gases whichhave passed .the diagram, Fig. 5. The apparatus is one which includesfour combustion chambers and rotors having two openings. In such anapparatus, there are two cycles of operation in each chamber for eachrevolution of the rotor, so that each cycle is carried out in a periodof time corresponding to of rotor movement. The diagram shows that theexhaust opening 30a of exhaust rotor 30 has Just opened the exhaustorifice of combustion chamber I and explosive discharge of the contentsof the chamber is occurring. In such explosive discharge, the burnedgases issue from the combustion chamber as a mass, leaving a potentialvoid behind them adjacent the inlet port. In the apparatus, to which thediagram, Fig. 5, applies, the volume of the individual combustionchambers and the speed of rotation of the rotors are such that theexhaust orifice is opened, the acceleration of the burned gases withinthe chamber is completed, and the mass movement of gases starts withina. period corresponding to 22 of rotor travel.

At the time that the mass movement of the exhaust gases-from the chamberstarts, or shortly thereafter, the opening 23a of the inlet rotor 23moves into registry with the inlet orifice of chamber I at such speedthat air under pressure from receiver ll enters the chamber inaccordance with the phenomenon of implosive inlet. The exhaust opening30a is of such length as to overlap the inlet opening 23a, so that fora, period corresponding, for example, to 40 to 45 of rotor movement,both the inlet and the exhaust orifice of chamber I are open and air ispassing through the chamber and into the exhaust passage and exhaustpipe leading therefrom. When a predetermined amount of cooling air haspassed determined amount of cooling air has passed through the chamber,the exhaust orifice is quickly closed by rotor 30, while the inletorifice continues open. The sudden closing of the exhaust orificeproduces a ramming effect of the inlet air within the chamber, so thatthe pressure of the air therein exceeds the pressure of the air at itssource. The inlet orifice is then closed before the supercharged airwithin the chamber can escape through the inlet orifice. Thissupercharging of the chamber is in accordance with the method disclosedin my Patent 2,281,585. The operations of explosive exhaust, the passageof air through the chamber, and the supercharging of the chamber occurin a period of time corresponding to about 92 of rotor travel and, inthe remaining period of the cycle corresponding to about 88 of rotortravel, the fuel is injected and ignited and the combustion occurs.

As shown in Fig. 5, the cycles of operation in chambers I and III of theapparatus are in phase and the cycles in chamber II and IV are also inphase but half a cycle behind the cycles in chambers I and III. Thisarrangementis desirable for use in the power plant shown in Fig. '7, inthat exhaust gas masses issuing simultaneously from chambers I and IIIstrike the blades of the impulse turbine wheel 55 at diametricallyopposite points, so that the action is balanced. Similarly, the exhaustgas masses issuing from chambers II and IV strike diametrically disposedblades of the wheel.

Apparatus of the type described, in which there are two cycles ofoperation in each chamber during one rotation of the rotors, ispreferred for operation with low inlet air pressure and low rotor speed,since there may be a relatively long overlap of the inlet and exhaustorifice rotor openings and, therefore, more time for the passage of airthrough each combustion chamber. Th air thus passed through a chambercools the chamber and also reduces the temperature of the exhaust gaswithin the exhaust gas receiver. Such a reduction of the temperature orthe compressed gases in that receiver is necessary, since the exhaustgases at the temperature, at which they leave the combustion chambers,are too hot for passage through the turbines 42 or 63 without doingdamage thereto. The introduction of air through each chamber into thereceiver reduces the temperature of the gases stored under pressurewithin the receiver, but the potential energy of the stored gasesremains substantially the same in each unit of time, because of theadded weight of air introduced into the receiver within that unit oftime.

The total quantity of air passing through a chamber, when both the inletand exhaust orifices are open, depends on the length of the rotoropenings, the pressure of the inlet receiver air, and the speed ofrotation of the rotors. By forming the chambers with the orifices intheir side walls, it is possible to use rotors of the constructiondescribed for controlling those orifices, and numerous advantages arethereby afforded, as follows. The dimension of an orifice in a directionlengthwise of its chamber may be substantially longer than the diameterof the chamber, so that, although the orifice has a cross-sectional areaequal to the transverse cross-sectional area of the chamber, thedimension of the orifice in a direction transverse to the chamber orcircumferentially of the rotors is less than the diameter of thechamber. As a result, less angular movement of a rotor is required toopen the orifice and the orifice may be opened within the criticalconditions for explosive exhaust or implosive inlet without thenecessity of driving the rotor at an excessive peripheral speed. Theminimum speed, at which the rotors may be driven, is that necessary toopen the orifices within about V of a second or less, and the maximumspeed, at which the rotors may be driven, is that at which it ispossible to pass a suflicient amount of air through each chamber aftereach explosive exhaust therefrom to effect the reduc-' tion intemperature of the exhaust gases necessary to protect the turbine. Itwill be apparent that the maximum rotor speed depends on the pressure ofthe inlet air, since with a higher inlet pressure, a larger amount ofair may be passed through a chamber in a given interval.

The formation of the chambers with the orifices in their side walls andfacing outwardly has a further advantage in that the orifices can beopened by openings in the cylindrical or conical portions of the rotors.With such a rotor construction, ample room is available between therotor openings and the rotor shaft for the provision of sealing means toprevent escape of gases from the chambers toward the shaft. Also, theopening and closing of the orifices by the rotation of the rotors is ata maximum rate for a.

, pressure in excess of the supply pressure.

given centrifugal force applied to the rotors. With the rotor openingsformed in the cylindrical or conical portions of the rotors, space isavailable for large size openings.

The diagram, Fig. 6, illustrates the sequence 01' operations in anotherform of the new apparatus. In the modified apparatus, there are fourcombustion chambers and each rotor has three openings, so that eachcycle of operations within a chamber occurs within a periodcorresponding to 120 of rotor travel. The diagram, Fig. 6, shows anexhaust opening 30b in registry with the exhaust orifice of combustionchamber I and explosive exhaust of the burned gases from the chamberoccurring. In the apparatus, to which the diagram, Fig. 6, applies, thevolume of the individual combustion chambers and the speed of rotationof the rotors are such that each explosive exhaust occurs during aperiod corresponding to 18 of rotor travel and, at the end of thatperiod, the burned gases have stopped reacting on the chamber wallsadjacent the inlet orifice and are leaving the chamber as a mass with apotential void behind them. At the end of the period, an opening 23b ofthe inlet rotor moves into registry with the inlet orifice of chamber I,so rapidly that implosive inlet of fresh air into the chamber occurs. Atthis time, the exhaust opening 3% is still in registry with the exhaustorifice and, for a period corresponding, for example, to 43 of rotortravel, both orifices are open, so that fresh air may pass through thechamber and into the exhaust pipe. At the end of the 43 period, theexhaust orifice begins to close while the inlet orifice remains openand, after a period corresponding to 18 of rotor travel, the exhaustorifice is fully closed and the inlet orifice begins to close, so thatair is trapped in the chamber at a During the next period correspondingto 41 of rotor travel, fuel is injected into the chamber to form acombustible mixture, which is ignited and burned, and the exhaustorifice is opened by the registration of an opening 30b in the exhaustrotor with the orifice.

While the cycle of operations above described is taking place incombustion chamber I, corresponding cycles are occurring in chambers II,III and IV, but those cycles are out of phase with the cycle in chamberI. Thus, at the time that explosive exhaust from chamber I is occurring,as illustrated, injection and combustion are occurring in chamber 11,supercharge is occurring in chamber III, and both orifices of chamber IVare open, so that air is passing through the chamber. In the apparatusillustrated in Fig. 6, three cycles of operation occur in each chamberper rotation of the rotor, so that twelve volumes of burned gases areproduced from the apparatus per rotation of the rotors. An apparatusoperating in accordance with Fig. 6 is suitable for operation with inletair at a higher pressure than the apparatus, the operation of which isrepresented by Fig. 5, because, with a given rotor speed, the timeavailable for a cycle of operation of the Fig. 6 apparatus is less thanthat available for a cycle in the Fig. 5 apparatus. Accordingly, inorder to pass the necessary quantity of air through the chambers in theFig. 6 apparatus, the pressure of the air supplied is increased. Thepressure and the temperature within each chamber during the injectionperiod are correspondingly increased and this increases the speed ofcombustion of the fuel.

In the apparatus illustrated, air is supplied under pressure to thecombustion chambers to produce a high output, but the chambers may besupplied with atmospheric air, if desired. Implosive inlet does notdepend on the use oi air under pressure but is obtained whenever gasfrom a source at one pressure is discharged therefrom into a space at alower pressure through an orifice of critical dimensions opened within acritical time limit, as explained in my Patent 2,281,585. When thechambers are operated with explosive exhaust, the mass movement of theburned gases from each chamber leaves behind a potential void, which isthus a space in which the gas pressure is lower than atmospheric. Byemploying an inlet orifice of the critical size and opening such anorifice within the critical time interval, it is, accordingly, possibleto obtain implosive inlet into the chamber with the air supply atatmospheric pressure. When the air supplied is under a pressure andimplosive inlet is utilized, the phenomenon is the same but the level ofpressure throughout the entire system is raised by an amountcorresponding to the increased pressure of the source and the output iscorrespondingly increased. By introducing air into the chamber inaccordance with implosive inlet, it is readily possible in practice, asexplained in Patent 2,281,585, to supercharge each chamber to anabsolute pressure of 1.5 or more times the absolute pressure of thesource.

In the apparatus illustrated, a combustible mixture is produced in eachchamber by injection of the fuel into the charge of air within thechamber but, if desired, it is possible to supply of a fuel-air mixture,such as carbureted air or a mixture of air and pulverized solid fuel.The production of the combustible charges in the chambers by fuelinjection is preferred, however, since it permits the passage of freshair through each chamber after the combustion of each charge therein. Ifthe fuel is introduced with the air rather than by injection, a quantityof fuel-air mixture should be passed through each chamber, aftercombustion of each charge, to cool the chamber and lower the temperatureof the exhaust gases, and the fuel in the mixture thus passed throughthe chamber is wasted.

When the burned gases produced by the combustion of a charge in achamber of the apparatus are discharged by explosive exhaust, thechamber is self-cleaning, since the burned gases leave the chamber as amass. The air admitted by implosive inlet is not utilized, as inordinary twostroke cycle internal combustion engines, to scavenge thechamber and discharge residual burned gases therefrom, since no suchscavenging is necessary. A portion of the air admitted during implosiveinlet is used, as described, to cool the chamber and lower thetemperature of the exhaust gases, while the remainder provides the aircontent of the next charge in the chamber.

In the new apparatus, the speed of rotation of the rotors controls theamount of gas delivered per unit of time and thus controls the poweroutput. Since the speed of rotation of the rotors may be varied withinthe limits above explained, the apparatus is highly flexible inoperation. As the speed of rotation of the rotors is increased,

the inlet air pressure may be increased to in- 12 apparatuscontainingfour chambers can be built to produce a high output and the output ofsuch an apparatus can be readily increased by increasing the number orsize of the combustion chambers, while maintaining the peripheral speedof the rotors within acceptable limits.

The gas producing apparatus, made up of one or more elongated chambers,each having an inlet orifice and an outlet orifice at opposite ends inits side wall, and a pair of rotors for controlling the orifices, may beoperated in accordance with the disclosure of my Patent 2,281,585 as ameans for producing gas at a pressure higher than that of the gassupplied thereto, even though there is no combustion within thechambers. For this purpose, the gas under super-atmospheric pressure isadmitted to each chamber in accordance with the conditions for implosiveinlet and the gas is trapped in the chamber at a pressure of 1.5 or moretimes the pressure of the supply. The supercharged contents of thechamber are then discharged in accordance with the conditions forexplosive exhaust and with the succeeding charge introduced by implosiveinlet, as soon as the gases within the chamber stop reacting upon thechamber walls and begin to issue from the chamber as a mass, leaving apotential void behind.

The gas producing apparatus, in the constructions illustrated, includesfour chambers, but it may be constructed with one chamber or more, asdesired. The number of openings in the rotors may also be varied, solong as the apparatus operates as described.

I claim:

1. An apparatus for producing gases under pressure, which comprises thecombination of an elongated chamber of substantially uniformcrosssection from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theexhaust orifice having such an area in relation to the cross-sectionalarea of the chamber as to be suitable for explosive exhaust operation, apair of rotors mounted at opposite ends of the chamber for rotation on acommon axis, each rotor having a peripheral section overlying andnormally closing the adjacent orifice, each rotor having at least oneopening in said section registrable with the adjacent orifice and of anaxial dimension substantially equal to the axial dimension of said adjacnt orifice and a circumferential dimension substantially greater thanthat of said orifice, the openings in the rotors being angularly offsetbut overlapping with the opening in the rotor at the exhaust end of thechamber leading, means for rotating the rotors in unison and at such aspeed that the exhaust orifice is opened within the critical conditionsfor explosive exhaust, and means for introducing fuel into the chamber.

2. An apparatus for producing gases under pressure. which comprises thecombination of an elongated chamber of substantially uniformcross-section from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theorifices being of such area in relation to the cross-sectional area ofthe chamber as to be suitable for implosive inlet and explosive exhaustoperation, respectively, a pair of rotors mounted at opposite ends ofthe chamber for rotation on a common axis, each rotor having aperipheral section overlying and normally closing the adjacent orifice,each rotor having at least one opening in said section registrable withthe adjacent l3 orifice and of an axial dimension substantially equal tothe axial dimension of said adjacent orifice and a circumferentialdimension substantially greater than that of said orifice, the openingsin the rotors being angularly offset but overlapping withthe opening inthe rotor at the exhaust end of the chamber leading, means for rotatingthe rotors in unison and at such a speed that the inlet and exhaustorifices are opened within the critical conditions for implosive inletand explosive exhaust, respectively, and means for introducing fuel intothe chamber.

3. An apparatus for producing gases under pressure, which comprisesthecombination of an elongated chamber of substantially uniformcross-section from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theorifices being of such area in relation to the cross-sectional area ofthe chamber as to be suitable for implosive inlet and explosive exhaustoperation, respectively, a pair of rotors mounted at opposite ends ofthe chamber for rotation on a common axis, each rotor having aperipheral section overlying and normally closing the adjacent orifice,each rotor having at least one opening in said section registrable withthe adjacent orifice and of an axial dimension substantially equal tothe axial dimension of said adjacent orifice and a circumferentialdimension substantially greater than that of said orifice, the openingsin the rotors being angularly offset but overlapping with the opening inthe rotor at the exhaust end of the chamber leading, means for rotatingthe rotors in unison and at such a speed that the inlet and exhaustorifices are opened within the critical conditions for implosive inletand explosive exhaust, respectively, and means for supplying air underpressure to the chamber through the inlet orifice.

4. An apparatus for producing gases under pressure, which comprises thecombination of an elongated chamber of substantially uniformcross-section from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theorifices being of such area in relation to the cross-sectional area ofthe chamber as to be suitable for implosive inlet and explosive exhaustoperation, respectively, a pair of rotors mounted at opposite ends ofthe chamber for rotation on a common axis, each rotor having aperipheral section overlying and normally closing the adjacent orifice,each rotor having at least one opening in said section registrable withthe adjacent orifice and of an axial dimension substantially equal tothe axial dimension of said adjacent orifice and a circumferentialdimension substantially greater than that of said orifice, the openingsin the rotors being angularly offset but overlapping with the opening inthe rotor at the exhaust end of the chamber leading, means for rotatingthe rotors in unison and at such a speed that the inlet/and exhaustorifices are opened within the critical conditions for implosive inletand explosive exhaust, respectively, means for introducing fuel into thechamber, an exhaust conduit leading from the exhaust orifice and soformed as to provide a free passage for exhaust gas masses travelingtherethrough, and means for supplying air under pressure to the chamberthrough the inlet orifice, the circumferential dimensions of the rotoropenings and the speed of the rotors being such that, followingexplosive exhaust of each exhaust gas mass from the chember, a portionof air entering the chamber by implosive inlet passes through thechamber and into the conduit and is prevented from returning into thechamber by the closing of the exhaust orifice.

5. An apparatus for producing gases under pressure, which comprises thecombination of an elongated chamber of substantially uniformcross-section from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theexhaust orifice having such an area in relation to the cross-sectionalarea of the chamber as to be suitable for explosive exhaust operation, apair of rotors mounted at opposite ends of the chamber for rotation on acommon axis, each rotor having a peripheral section overlying andnormally closing the adjacent orifice, each rotor having at least oneopening in said section registrable with the adjacent orifice and of anaxial dimension substantially equal to the axial dimension of saidadjacent orifice and a circumferential dimension substantially greaterthan that of said orifice, the openings in the rotors being angularlyofiset but overlapping with the opening in the rotor at the exhaust endof the chamber leading, means for rotating the rotors in unison and atsuch a speed that the exhaust orifice is opened within the criticalconditions for explosive exhaust, means for supplying air under pressureto the chamber through the inlet orifice, and means for introducing fuelinto the chamber.

6. An apparatus for producing gases under pressure, which comprises thecombination of an elongated chamber of substantially uniformcross-section from end to end and having a single inlet orifice and asingle exhaust orifice in its side wall at opposite ends thereof, theexhaust orifice having such an area in relation to the cross-sectionalarea of the chamber as to be suitable for explosive exhaust operation, apair of rotors mounted at opposite ends of the chamber for rotation on acommon axis, each rotor having a peripheral section overlying andnormally closing the adjacent orifice, each rotor having at least oneopening in said section registrable with the adjacent orifice and of anaxial dimension substantially equal to the axial dimension of saidadjacent orifice and a circumferential dimension substantially greaterthan that of said orifice, the openings in the rotors being angularlyoffset but overlapping with the opening in the rotor at the exhaust endof the chamber leading, means for rotating the rotors in unison and atsuch a speed that the exhaust orifice is opened within the criticalconditions for explosive exhaust, means for supplying air under pressureto the chamber through the inlet orifice, means for introducing fuelinto the chamber, and an exhaust conduit leading from the exhaustorifice and so formed as to provide a free passage for exhaust gasmasses traveling therethrough, the circumferential dimensions of therotor openings and the speed of the rotors being such that, followingexplosive exhaust of each exhaust gas mass from the chamber, a portionof air entering the chamber passes through the chamber and into theconduit and is prevented from returning into the chamber by the closingof the exhaust orifice.

7. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from end to end and disposed withtheir axes parallel, the

chambers lying symmetrically with respect to a chamber as to be suitablefor explosive exhaust operation, a pair of rotors mounted at oppositeends of the group of chambers for rotation on said common axis, eachrotor having a peripheral section overlying and normally closing theadjacent orifices and each rotor having at least one opening in saidperipheral section registrable with the adjacent orifices and ofan,axial dimension substantially equal to that of said adjacent orificesand a circumferential dimension substantially greater than that of saidadjacent orifices, the circumferential length of said opening in eachrotor being shorter than the distance between like orifices inadjacent'chambers, corresponding openings in the rotors being angularlyofiset but overlapping with the opening in the rotor at the exhaust endsof the chambers leading, means for rotating the rotors in unison and atsuch a speed that the exhaust orifices of the chambers are opened withinthe critical conditions for explosive exhaust, and means for introducingfuel into the chambers.

8. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from.

end to end and disposed with their axes parallel, the chambers lyinsymmetrically with respect to a common axis and each having a singleinlet orifice and a single exhaust orifice in its side wall at oppositeends thereof, the inlet orifices being alike and lying at one end of thegroup of chambers and the exhaust orifices being alike and lying at theother end of the group of chambers, each exhaust orifice having such anarea in relation to the cross-sectional area of its chamber as to besuitable for explosive exhaust operation, a pair of rotors mounted atopposite ends of the group of chambers for rotation on said common axis,each rotor having a peripheral section overlying and normally closingthe adjacent orifices and each rotor having at least oneopening in saidperipheral section registrable with the adjacent orifices and of anaxial dimension substantially equal to that of said adjacent orificesand a circumferential dimension substantially greater than that of saidadjacent orifices, the circumferential length of said opening in eachrotor being shorter than the distance between like orifices in adjacentchambers, corresponding openings in the rotors being angularly offsetbut overlapping with the opening in the rotor at the exhaust ends of thechambers leading, means for rotating the rotors in unison and at such aspeed that the exhaust orifices of the chambers are opened within thecritical conditions for explosive exhaust, means for supplying air underpressure to the several chambers through their inlet orifices, and meansfor introducing fuel into the several chambers.

9. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from end to end and disposed withtheir axes parallel, the chambers lying symmetrically with respect to acommon axis and each having a single inlet orifice and a single exhaustorifice in its side wall at opposite ends thereof, the inlet orificesbeing alike and lying at one end of the group of chambers and theexhaust orifices being alike and lying at the other end of the group ofchambers, each exhaust orifice having such an area in re lation to thecross-sectional area of its chamber as to be suitable for explosiveexhaust operation, a pair of rotors mounted at opposite ends of thegroup of chambers for rotation on said common axis, each rotor having aperipheral section overlying and normally closing the adjacent orificesand each rotor having at least one opening in said peripheral sectionregistrable with the adjacent orifiices and of an axial dimensionsubstantially equal to that of said adjacent orifices and acircumferential dimension substantially greater than that of saidadjacent orifices, the circumferential length of said opening in eachrotor being shorter than the distance between like orifices in adjacentchambers, corresponding openings in the rotors being angularly ofisetbut overlapping, with the opening in the rotor at the exhaust ends ofthe chambers leading, means for rotating the rotors in unison and atsuch a speed that the exhaust orifices of the successive chambers areopened within the critical conditions for explosive exhaust, means forsupplying air under pressure to the several chambers through their inletorifices, means for introducing fuel into the several chambers, and aseparate exhaust gas conduit leading from the exhaust orifice of eachchamber and so formed as to provide a free passage for exhaust gasmasses traveling therethrough, the circumferential dimensions of therotor openings and the rotor speed being such that, following explosiveexhaust of each exhaust gas mass from a chamber, a portion of airentering the chamber through its inlet orifice passes through thechamber into the exhaust conduit and is prevented from returning intothe chamber by closing of the exhaust orifice of said chamber.

10. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from end to end and disposed withtheir axes parallel, the chambers lying symmetrically with respect to acommon axis and each having a single inlet orifice and a single exhaustorifice in its side wall at opposite ends thereof, the inlet orificesbeing alike and lying at one end of the group of chambers and theexhaust orifices being alike and lying at the other end of the group ofchambers, each inlet orifice and each exhaust orifice having such anarea in relation to the cross-sectional area of its chamber as to besuitable for implosive inlet and explosive exhaust operation,respectively, a pair of rotors mounted at opposite ends of the group ofchambers for rotation on said common axis, each rotor having aperipheral section overlying and normally closing the adjacent orificesand each rotor having at least one opening in said peripheral sectionregistrable with the adjacent orifices and of an axial dimensionsubstantially equal to that of the adjacent orifices and acircumferential dimension substantially greater than that of saidorifices, the circumferential length of the opening in each rotor beingshorter than the distance between like orifices in adjacent chambers,corresponding openings in the rotors being offset but overlapping withthe opening in the rotor at the e aust ends of the chambers leading,means for rotating thev rotors in unison and at such a speed that theinlet and exhaust orifices oi the chambers are opened within thecritical conditions for implosive inlet and explosive exhaust,respectively, and means for supplying the chambers with air underpressure ,through their inlet orifices.

11. An apparatus for producing gases under pressure, which" comprisesthe combination of a bers and the exhaust orifices being alike and lyingat the other end of the group of chambers, eachinlet orifice and eachexhaust orifice having 'such an area in relation to the cross-sectionalarea of its chamber as to be suitable for implosive inlet and explosiveexhaust operation, respectively, a pair of rotors mounted at oppositeends of the group of chambers for rotation on saidcommon axis, eachrotor having a peripheral section overlying and normally closing theadjacent orifices and each rotor having at least one opening in saidperipheral section registrable with the adjacent orifices and of anaxial dimension substantially equal to that of the adjacent orifices anda circumferential dimension substantially greater than that of saidorifices, the circumferential length of the opening in each rotor beingshorter than the distance between like orifices in adjacent chambers,corresponding openings in the rotors being ofiset but overlapping withthe opening in the rotor at the exhaust ends of the chambers leading,means for rotating the rotors in unison and at such a speed that theinlet and exhaust orifices of the chambers are opened within thecritical conditions for implosive inlet and explosive exhaust,respectively, and means for introducing fuel into the chambers insuccession.

12. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from end to end and disposed withtheir axes parallel, the chambers lying symmetrically with respect to acommon axis and each having a single inlet orifice and a single exhaustorifice in its side wall at opposite ends thereof, the inlet orificesbeing alike and lying at one end of the group of chambers and theexhaust orifices being alike and lying at the other end of the group ofchambers, each inlet orifice and each exhaust orifice having such anarea in relation to the cross-sectional area of its chamber as to besuitable for implosive inlet and explosive exhaust operation,respectively, a pair of rotors mounted at opposite ends of the group ofchambers for rotation on said common axis, each rotor having aperipheral section overlying and normally closing the adjacent orificesand each rotor having at least one opening in saidv peripheral sectionregistrable with the adjacent orifices and of an axial dimensionsubstantially equal to that of the adjacent orifices and a,circumferential dimension substantially greater than that ofsaidorifices, the circumferential length of the opening in each rotorbeing shorter than the distance between like orifices in adjacentchambers, corresponding openings in the rotors being offset butoverlapping with the opening in the rotor at the exhaust ends of thechambers leading, means for rotating the rotors in unisonand at such aspeed that the inlet and exhaust orifices of the successive chambers areopened within the critical conditions for implosive inlet and explosiveexhaust, respectively, means for supplying the chambers with air underpressure through their inlet orifices, means for introducing fuel intothe chambers, and a separate exhaust conduit leading from therexhaustorifice of each chamber and formed to provide a free passage'for exhaustgas masses traveling therethrough, the circumferential dimensions of-therotor openings and the speed of therotors'being such'that, followingexplosive exhaust oteach exhaust gas mass from the chamber, a portion ofair entering the chamber passes through the chamber and into the conduitof said chamber and is prevented from returning into the chamber by theclosing of the exhaust orifice. 1

13. An apparatus for producing gases under pressure, which comprises thecombination of a plurality of like elongated combustion chambers ofsubstantially uniform cross-section from end to end and disposed withtheir axes parallel, the chambers lying symmetrically with respect to acommon axis and each having a single inlet orifice and single exhaustorifice in its side wall at opposite ends thereof, the inlet orificesbeing alike and lying at one end of the group of chambers and theexhaust orifices being alike and lying at the other end of the group ofchambers, each exhaust orifice having such an area in relation to thecross-sectional area of its chamber as to be suitable for explosiveexhaust operation, a pair of rotors mounted at opposite ends of thegroup of chambers for rotation on said common axis, eachrotor having aperipheral section overlying and normally closing the adjacent orificesand each rotor having a plurality of openings in said peripheral sectionregistrable successively with the adjacent orifices, each opening in arotor having an axial dimension substantially equal to that of theadjacent orifices and a circumferential dimension substantially greaterthan that of said orifices, the circumferential length of each openingin a rotor being shorter than the distance between like orifices inadjacent chambers, the openings in each rotor being paired with those inthe other with said openings in a pair being angularly offset butoverlapping'and with the opening in the rotor at the exhaust ends of thechambers leading, means for rotating the rotors in unison and at such aspeed that the exhaust orifices are opened within the criticalconditions for explosive exhaust, the number of chambers and the numberof pairs of openings in the rotors being such that the exhaust orificesof diametrically disposed chambers are simultaneously opened, a separateexhaust conduit leading from each exhaust orifice and formed to providea free passage for exhaust gas masses traveling therethrough, means forintroducing fuel into the chambers, and an impulse turbine having acasing with equiangularly spaced inlets, to which the exhaust conduitslead, and a wheel receiving impulses diametrically from exhaust gasestraveling through conduits from diametrically disposed chambers.

MICHEL KADENACY.

(References on following page) 9 REFERENCES crrEn The followingreferences are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date Loftus Dec. 6, 1910 HoizwarthJuly 16, 1912 Rich Dec. 21, 1915 Lincoln Dec. 24, 1918 10 Duryea. Aug.19, 1919 Kadenacy May 5, 1942 Number 20 FOREIGN PATENTS Country DateGreat Britain Aug. 18, 1930 Great Britain May 3, 1934 Germany Dec. 21,1923 Germany Mar. 28, 1925 France Feb. 9, 1910 France May 28, 1927Austria Aug, 26, 1918

